| 摘要 |
A combustion chamber arrangement is described for operating a gas turbine, with a combustion chamber wall (1) which encloses the combustion chamber space (3) and in the region of the combustion chamber outlet encloses a flow passage for hot gases which develop inside the combustion chamber, has a combustion chamber wall edge (4) which freely terminates in the axial flow direction of the hot gases and with an axial overlapping (5) and also with a radial clearance (6), leads downstream into a hot gas housing (2) which radially encompasses the combustion chamber wall (1) and indirectly or directly upon which are attached individual collar-like fastening means (7) which project upstream over the hot gas housing (2), are arranged in a distributed manner in the circumferential direction of the hot gas housing (2), and serve for axial fixing of an annular seal (9) which can be attached on the outer side on the combustion chamber wall (1) upstream to the combustion chamber wall edge (4) and completely encompasses the combustion chamber wall (1) in the circumferential direction, the seal comprising a multiplicity of individual sealing segments (10) which on the end face can be joined to each other in each case in pairs via connecting structures (11), on one side axially indirectly or directly adjoin the hot gas housing (2) and with the outer-side combustion chamber wall (1) delimits axially oriented flow passages (12) which on one side lead into an annular spatial area (13) which is radially delimited by means of the axially mutually overlapping combustion chamber wall (1) and hot gas housing (2).
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